Abstract: A system for wirelessly controlling marker lights comprising a remote controller comprising a transmitter and one or more marker lights. Each of the marker lights comprise a receiver and processing means, and each of the marker lights have a configuration mode in which the processing means is adapted to cause the receiver to wirelessly receive data from the transmitter. This data comprises one or more group identifiers to assign one or more groups to the marker light. In addition, the processing means of each of the marker lights is adapted to cause the receiver to wirelessly receive one or more commands from the transmitter for controlling the operation of the marker light. The processing means is adapted to carry out the command when the commands comprise the same one or more group identifiers that correspond to the one or more groups to which the marker light was assigned.

Abstract: A system for wirelessly controlling marker lights comprising a remote controller comprising a transmitter and one or more marker lights. Each of the marker lights comprise a receiver and processing means, and each of the marker lights have a configuration mode in which the processing means is adapted to cause the receiver to wirelessly receive data from the transmitter This data comprises one or more group identifiers to assign one or more groups to the marker light. In addition, the processing means of each of the marker lights is adapted to cause the receiver to wirelessly receive one or more commands from the transmitter for controlling the operation of the marker light. The processing means is adapted to carry out the command when the commands comprise the same one or more group identifiers that correspond to the one or more groups to which the marker light was assigned.

Abstract: The invention concerns a Ni based alloy suitable for single 5 crystalline, directionally solidified or polycrystalline components to be used at high temperatures. The alloy is a?/ alloy and consists of different alloying elements within defined ranges. Among other defined ranges of elements, the alloy contains Pd in a significant amount sufficient to provide the alloy with an improved resistance against hydrogen embrittlement. The invention also concerns a component designed for use as a component in a high temperature environment. Furthermore, the invention concerns a gas turbine arrangement. Moreover, the invention concerns the use of Pd for providing an alloy with improved resistance against hydrogen embrittlement. The inclusion of two or more rare earth elements in the alloy provides enhanced bondcoat compatibility.

Abstract: An improved nickel-based superalloy having high corrosion and oxidation resistance and good compatibility with a thermal barrier coating. The enhanced oxidation resistance and compatibility with the thermal barrier coating results from the inclusion of two or more rare earth elements. The superalloy is useful for the fabrication of components for a gas turbine.

Abstract: The invention concerns a Ni based alloy suitable for single 5 crystalline, directionally solidified or polycrystalline components to be used at high temperatures. The alloy is a?/ alloy and consists of different alloying elements within defined ranges. Among other defined ranges of elements, the alloy contains Pd in a significant amount sufficient to provide the alloy with an improved resistance against hydrogen embrittlement. The invention also concerns a component designed for use as a component in a high temperature environment. Furthermore, the invention concerns a gas turbine arrangement. Moreover, the invention concerns the use of Pd for providing an alloy with improved resistance against hydrogen embrittlement. The inclusion of two or more rare earth elements in the alloy provides enhanced bondcoat compatibility.

Abstract: Aspects of the invention are directed to a turbine blade assembly and an associated method of manufacture. The turbine blade assembly can include: (a) a unitary structure having an airfoil and a primary root portion; (b) a separately-formed platform; and (c) a secondary root portion that cooperates with the primary root portion to define a root. The platform can be secured in place between the structure and the secondary root portion. In a preferred embodiment, the structure can be formed by casting, and the secondary root portion can be formed by powder metallurgy. Ideally, the structure is configured so as to avoid large changes in section size or to at least make such changes gradual, particularly in transitioning from the airfoil to the primary root portion. The turbine blade assembly can reduce the propensity for defects to form during the manufacturing process. Thus, higher casting yields can be realized.

Abstract: Aspects of the invention relate to a modular turbine vane assembly. The vane assembly includes an airfoil portion, an outer shroud and an inner shroud. The airfoil portion can be made of at least two segments. Preferably, the components are connected together so as to permit assembly and disassembly of the vane. Thus, in the event of damage to the vane, repair involves the replacement of only the damaged subcomponents as opposed to the entire vane. The modular design facilitates the use of various materials in the vane, including materials that are dissimilar. Thus, suitable materials can be selected to optimize component life, cooling air usage, aerodynamic performance, and cost. Because the vane is an assemblage of smaller sub-components as opposed to one unitary structure, the individual components of the vane can be more easily manufactured and more intricate features can be included.

Abstract: A superalloy with enhanced coating compatibility. The alloy is a nickel-based alloy and may be used in various applications, such as the production of gas turbine components, due to its high strength. The alloys are highly oxidation resistant and have enhanced coating compatibility. The alloys may be used as an underlying substrate with a variety of different coatings, including thermal and environmental barrier coatings. The alloys may be produced using known casting and or alloy mastering techniques.

Abstract: A composite turbine disc includes a bore section providing a first set of mechanical and temperature resistance properties, and a rim section which provides a second set of mechanical and temperature resistance properties. The second set of mechanical properties and temperature resistance are superior to the first set of properties. An intermediate diaphragm section is disposed between the bore section and the rim section. The intermediate section has mechanical and temperature resistance properties in a range between the first and second set of properties.

Abstract: A hybrid component (30) having a cast single crystal superalloy portion (32) and an attached powder metallurgy material portion (34). The component may be a blade (30) of a gas turbine engine having a single crystal airfoil section and a powder metallurgy material root section. The powder metallurgy material may extend to form a core (36) within the airfoil section and may include cooling passages 38. The single crystal portion has a relatively simple geometry so that casting yields are optimized. The powder metallurgical portion includes the lower stressed and more complicated geometry sections of the component. A method of forming such a component includes casting the single crystal superalloy portion, then using that portion to form part of the mold for forming the powder metallurgy material portion.

Abstract: A nickel base powder metallurgy superalloy gas turbine engine disk for a compressor or turbine. The wrought powder metallurgy gas turbine engine disk has desirable fatigue crack growth resistance and a superior balance of tensile, creep rupture and low cycle fatigue strength characteristics. In one embodiment the disk defines a segregation free homogenous structure.